The orbital velocity of an artifical satellite in a circular orbit just above the earth's surface is `V_(0)`. For a satellite orbiting at an altitude of half of earth's radius, the orbital velocity is

Options

A. `(2)/(3)V_(0)`
B. `sqrt((2)/(3))V_(0)`
C. `(3)/(2)V_(0)`
D. `sqrt((3)/(2))V_(0)`

Answer

B

Explanation

`V_(0)=sqrt((GM)/(R )), V_(0)' = sqrt((GM)/((3)/(2)R)) therefore V_(0)' = sqrt((2)/(3))V_(0)`